JP2009531587A - Turbocharger - Google Patents

Abstract

  The present invention relates to a turbocharger (1) with a variable turbine geometry (VTG) comprising a plurality of guide blades (7). Each guide blade (7) has a blade lever (19, 19 '), in which case the central plane (Em2) of the intermediate region (24; 24') of this blade lever (19, 19 ') is the blade axis. The first end region (20; 20 ′) of the blade lever (19; 19 ′) and the second end of the blade lever (19, 19 ′) are displaced axially along the longitudinal axis (L) of the blade lever (19, 19 ′). It arrange | positions so that it may be located in a certain distance (a) from the center plane (Em1) of area | region (23; 23 '), Furthermore, 1st edge part area (20; 20') and 2nd edge part area (23; 23) In between, a recess (26; 26 ') is provided adjacent to the intermediate region (24; 24').

Description

  The present invention relates to a turbocharger according to the first stage of claim 1.

  A turbocharger of this type is known from EP 1 520 959 A1.

  In this turbocharger structure, the blade lever is configured as a machined part having a material cutting and removing portion, for example, a part to be milled.

  In contrast, an object of the present invention is a turbocharger according to the preceding paragraph of claim 1, wherein the special shape of the blade lever allows simpler and lower cost production of these parts with high dimensional accuracy. It is to provide a turbocharger that makes the method possible.

  This object is achieved by the features of claim 1.

  The structure according to the invention of the blade lever allows the lever for connection between the guide blade and the adjusting ring to be manufactured by stamping or extrusion, which simplifies the manufacturing process and reduces costs.

  The dependent claims contain advantageous developments of the invention.

  Further details, advantages and features of the invention will become apparent from the following description and drawings.

  FIG. 1 shows a turbocharger 1 according to the invention. The turbocharger 1 has a turbine housing 2 and a compressor housing 3 connected to the turbine housing 2 via a bearing housing 28. The housings 2, 3 and 28 are arranged along the rotation axis R. The turbine housing 2 is shown partially in section to clarify the arrangement of the blade support ring 6 and the radially outer guide cascade 18. The guide blade row 18 is formed by the blade support ring 6 and has a plurality of guide blades 7. The plurality of guide blades 7 are distributed over the entire circumference and have a blade shaft 8. As a result, a nozzle cross-sectional area that increases or decreases depending on the position orientation of the guide blade 7 is formed, and the exhaust gas of the engine is increased or decreased in the turbine rotor 4 located at the center on the rotation axis R. The compressor impeller 17 mounted on the same shaft is driven through the turbine rotor 4. The exhaust gas is supplied via the supply flow path 9 and is discharged from the center connection portion 10.

  An actuator 11 is provided for controlling the operation of the guide blade 7 and the position and orientation. Although the actuator 11 can itself be configured in any form, one preferred embodiment has a control housing 12 that controls the control action of the tappet element 14 attached thereto. Thus, the movement of the adjusting ring 5 provided behind the blade support ring 6 is converted into a slight rotational movement of the adjusting ring 5. A gap 13 for the guide blade 7 is formed between the blade support ring 6 and the annular portion 15 of the turbine housing 2. In order to allow the clearance 13 to be ensured, the blade support ring 6 has a spacer element 16 which is integrally molded. In principle, this type of spacer element 16 can be provided with some difference.

  FIG. 2 is a cross-sectional perspective view of the blade lever 19 according to the present invention, in which the blade lever 19 is engaged with the receiving recess 27 of the adjustment ring 5. The blade lever 19 according to the invention has a receiving bore 21 in its first end region 20 for receiving the shaft end of the blade shaft 8. In FIG. 2, the blade shaft 8 is symbolically indicated by its longitudinal axis L. An intermediate region 24 and a second end region 23 are adjacent to the receiving bore 21 of the blade lever 19 in the radial direction. The intermediate region 24 has a support surface 25 on the radially outer side, and this support surface 25 is supported by a support surface 31 opposite to the support portion 30 of the adjustment ring 5. As can be seen in FIG. 3, the support surface 31 is located inside the receiving recess 27 of the adjustment ring 5.

Further, FIG. 2 shows that the center plane E _M2 of the intermediate region 24 is shifted in the axial direction by a certain distance a along the longitudinal axis L of the blade shaft, and the first end region 20 and the second end region 23. It is clarified that they are arranged in parallel to the center plane E _M1 of the.

  Further, a recess 26 disposed adjacent to the intermediate region 24 is provided between the first end region 20 and the second end region 23.

  The adjusting ring 5 has one receiving recess 27 for each lever head 22, which can be seen in FIG. As can be seen in FIGS. 2, 3 and 4, the receiving recess 27 of the adjustment ring 5 has a stopper wall 29 which is arranged radially outward.

  Furthermore, the shape of the blade lever 19 and the structure of the recess 26 extending in the shape of a partial arc can be understood by looking at FIGS. 2, 3 and 5 together. As can be seen, the side wall surfaces 36, 37 of the receiving recess 27 constitute a limit for the rotational movement of the intermediate region 24 of the blade lever 19 in the circumferential direction U of the adjustment ring 5.

  6-9 show a second embodiment of the blade lever 19 'and the adjustment ring 5' of the present invention. The same reference numerals are assigned to all parts that match the first embodiment, but a prime symbol (') is added.

As can be seen in FIG. 7, the adjustment ring 5 ′ differs from the adjustment ring 5 of the first embodiment in that it has a receiving recess 27 ′ that penetrates the full thickness W of the annular wall. Furthermore, the adjustment ring 5 ′ has a plurality of raised portions 34 having a wall thickness or width _BE smaller than the adjustment ring 5 ′. Wall thickness or radial width of the adjusting ring 5 'is shown by dimension B _V.

  In addition, the blade lever 19 ', as seen in FIGS. 7 and 9, has rounded shoulders 32, 33 that project beyond its width B in the middle region 24' on both sides thereof. Is different from the blade lever 19 of the first embodiment. Furthermore, in this embodiment, the intermediate region 24 of the blade lever 19 'is supported in the radial direction exclusively by the inner surface 35 of the adjustment ring 5' defined by the inner diameter of the adjustment ring.

  As a result of the above-described shape of the blade levers 19, 19 ', it is possible to mold the component as a precision stamped part.

  To complement the above disclosure, the drawing representations of the present invention in FIGS.

1 shows a perspective view of a turbocharger according to the invention, partly in section. FIG. 3 is a partial cross-sectional perspective view of the adjustment ring and blade lever according to the present invention, showing the blade lever engaged with the adjustment ring. It is a top view of the receiving recessed part of an adjustment ring, Comprising: The state in which the blade lever by this invention is engaging with the said adjustment ring is shown. FIG. 4 shows a perspective view of an adjustment ring having a receiving recess formed by the “extrusion” manufacturing method for a blade lever according to the present invention. 1 shows a perspective view of a blade lever according to the invention. FIG. 3 shows a perspective view corresponding to FIG. 2 of a part of a second embodiment of an adjustment ring and blade lever according to the invention. FIG. 4 shows a plan view corresponding to FIG. 3 of the adjustment ring and blade lever according to the invention. FIG. 7 shows a perspective view of the adjustment ring according to FIG. 6 corresponding to FIG. 4. FIG. 3 shows a perspective view of a second embodiment of a blade lever according to the present invention.

Explanation of symbols

DESCRIPTION OF SYMBOLS 1 Turbocharger 2 Turbine housing 3 Compressor housing 4 Turbine rotor 5, 5 'Adjustment ring 6 Blade support ring 7 Guide blade 8 Blade shaft 9 Supply flow path 10 Axial connection 11 Actuator 12 Control housing 13 Gap 14 for guide blade 7 Tappet element 15 Annular portion of turbine housing 2 16 Spacer element / spacer cam 17 Compressor impeller 18 Guide blade row 19, 19 'Blade lever 20, 20' End region 21, 21 'Receiving perforation 22, 22' Lever head 23, 23 'End region 24, 24' Intermediate region 25 Support surface 26, 26 'Recess 27, 27' Receiving recess 28 Bearing housing 29 Stopper wall body 30 Support portion 31 Support surface 32, 33 Shoulder portion 34 Protruding portion 35 Inner surface 36, 36 'side Wall surface 37, 37 ′ Side wall surface B width, lever head B _E width, protruding portion B _V width, adjustment ring EM ₁ Center surface EM of first end region 20, 20 ′ and second end region 23, 23 ′ ₂ Center planes 24, 24 ′ center plane U circumferential direction of the adjustment ring 5, 5 ′

Claims (10)

A turbine housing (2) having a supply flow path (9) for exhaust gas,
-Having a turbine rotor (4) rotatably mounted in said turbine housing (2);
-With variable turbine geometry guide cascade (18),
A turbocharger (1) with variable turbine geometry (VTG);
The guide blade row (18) surrounds the turbine rotor (4) outward in the radial direction,
The guide blade row (18) has a blade support ring (6),
The guide blade row (18) has a plurality of guide blades (7) each having one blade axis (8), and the blade axis (8) has a longitudinal axis (L) of the blade axis and the blade Attached to the support ring (6),
Said guide cascade (18) has an adjusting ring (5; 5 ') operatively coupled to said guide blade (7); and
The guide blade row (18) has one blade lever (19; 19 ′) for each guide blade (7),
A turbocharger (1), wherein the blade lever (19; 19 ′)
Receiving bores (21; 21 ') arranged in the first end region (20) for one shaft end of the blade shaft (8) having a longitudinal axis (L);
Having a lever head (22, 22 ') in a second end region (23; 23') having the same center plane (E _M1 ) as the first end region (20; 20 '); and
Having an intermediate region (24; 24 ') provided with a support surface (25) for radial attachment of said adjusting ring (5; 5');
In turbocharger (1),
Said intermediate region (24; 24 ') center plane of the _{(E M2)} is the first end region (20; 20') and said second end region; center plane of the (23 23 ') _{(E M1)} With a certain distance (a) being shifted axially along the longitudinal axis (L) of the blade axis, and
Between the first end region (20; 20 ') and the second end region (23; 23'), a recess (26; 26 ') is adjacent to the intermediate region (24; 24'). A turbocharger (1) characterized by being provided.   The turbocharger (1) with variable turbine geometry (VTG) according to claim 1, characterized in that the intermediate region (24; 24 ') is of arcuate structure.   A support part (30) having a support surface (31) interacting with the support surface (25) is arranged below the receiving recess (27; 27 ') of the adjustment ring (5; 5'); A turbocharger (1) with a variable turbine geometry (VTG) according to claim 1.   The turbocharger (1) with variable turbine geometry (VTG) according to claim 3, characterized in that the support surface (25) is arranged inside the receiving recess (27; 27 ').   The receiving recess (27; 27 ') serves as a limit for the rotational movement of the intermediate region (24; 24') in the circumferential direction (U) of the adjusting ring (5; 5 ') as a side wall surface (36; Turbocharger (1) with variable turbine geometry (VTG) according to claim 3 or 4, characterized in that it has 36 'and 37; 37').   6. The inner surface (35) of the adjusting ring is provided exclusively as a radial support for the intermediate region (24; 24 ′) according to claim 3. Turbocharger (1) with variable turbine geometry (VTG). The adjusting ring (5; 5 ′) has a plurality of protruding portions (34), and the radial width (B _E ) of the protruding portions (34) is the radial width of the adjusting ring (5). Turbocharger (1) with variable turbine geometry (VTG) according to any one of the preceding claims, characterized in that it is smaller than (B _V ). A blade lever (19) for a turbocharger (1) with a variable turbine geometry (VTG),
A receiving bore (21; 21 ') arranged in the first end region (20; 20') for one axial end of the blade shaft (8) having a longitudinal axis (L);
Having a lever head (22; 22 ') in a second end region (23; 23') having the same center plane (E _M1 ) as the first end region (20; 20 ');
Having an intermediate region (24; 24 ') provided with a support surface (25) for radial mounting of the adjusting ring (5; 5');
In the blade lever (19),
Said intermediate region (24; 24 ') center plane of the _{(E M2)} is the first end region (20; 20') and said second end region; center plane of the (23 23 ') _{(E M1)} With a certain distance (a) being shifted axially along the longitudinal axis (L) of the blade axis, and
Between the first end region (20; 20 ') and the second end region (23; 23'), a recess (26; 26 ') is adjacent to the intermediate region (24; 24'). Blade lever (19) for turbocharger (1) with variable turbine geometry (VTG), characterized in that   A blade lever (19; 19 ') for a turbocharger (1) with a variable turbine geometry (VTG) characterized in that it has any of the features of claim 2.   An adjustment ring for a turbocharger (1) with a variable turbine geometry (VTG) characterized in that it has any of the features of claims 3-6.

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